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5 条记录 (耗时 0.015 秒)

    Compliant mounting system for turbine shrouds
    1.
    发明申请
    Compliant mounting system for turbine shrouds 有权
    符合涡轮机罩的安装系统

    公开(公告)号：US20060067813A1

    公开(公告)日：2006-03-30

    申请号：US10950750

    申请日：2004-09-27

    申请人： Adrian Allan ,  James Hadder ,  George Zurmehly

    发明人： Adrian Allan ,  James Hadder ,  George Zurmehly

    IPC分类号： F01D25/26

    CPC分类号： F01D9/02 ,  F01D25/246 ,  F01D25/26 ,  F05D2240/11 ,  Y10T29/4932 ,  Y10T29/49323 ,  Y10T29/49863 ,  Y10T29/49874

    摘要： The mounting of low expansion full ring shrouds in a turbine engine requires radial compliance to limit the stresses experienced by the shroud due to thermal growth differences between the shroud and its support. The present invention provides a method of providing radial compliance with no looseness in the mounting system. The compliant mounting system of the present invention also allows for axial motion of the shroud, should such motion be needed or desired. The lack of looseness in the shroud mounting system of the present invention results in an ability to achieve smaller tip clearances and thus better engine performance.

    摘要翻译： 在涡轮发动机中安装低膨胀全环护罩需要径向顺应性，以限制由于护罩和其支撑件之间的热膨胀差异导致的护罩所经受的应力。 本发明提供了一种在安装系统中提供没有松动的径向顺应性的方法。 如果需要或期望这样的运动，本发明的柔性安装系统还允许护罩的轴向运动。 在本发明的护罩安装系统中缺乏松动性导致能够实现更小的尖端间隙，从而获得更好的发动机性能。

    Cooled component with a featured surface and related manufacturing method
    2.
    发明授权
    Cooled component with a featured surface and related manufacturing method 失效
    冷却组件具有特色表面和相关制造方法

    公开(公告)号：US08109735B2

    公开(公告)日：2012-02-07

    申请号：US12270372

    申请日：2008-11-13

    申请人： Raymond Gage ,  Adrian Allan

    发明人： Raymond Gage ,  Adrian Allan

    IPC分类号： F04D29/38

    CPC分类号： B23P15/02 ,  F01D5/187 ,  F05D2260/202 ,  F05D2260/22141 ,  F05D2300/5024 ,  F23R2900/03045 ,  Y10T29/49336

    摘要： An improved type of cooled component is disclosed. The cooled components, such as turbine airfoils and combustors, have a base metal structural member, including a metal sheet or blank, with a featured surface. The features, such as fins, pins, and other protrusions, as well as divots, indentions, slots, channels, and holes, are formed by lithographic processes. The protrusions can be formed from a different material than the metal sheet or blank, preferably one with superior heat-conductive or oxidation properties. A related method of manufacturing is also disclosed.

    摘要翻译： 公开了一种改进型的冷却部件。 诸如涡轮机翼型和燃烧器的冷却部件具有贱金属结构件，包括具有特征表面的金属板或坯件。 通过光刻工艺形成诸如翅片，销和其它突起以及凹陷，凹陷，槽，通道和孔的特征。 突起可以由与金属板或坯料不同的材料形成，优选地具有优异的导热性或氧化性。 还公开了相关的制造方法。

    COOLED COMPONENT WITH A FEATURED SURFACE AND RELATED MANUFACTURING METHOD
    4.
    发明申请
    COOLED COMPONENT WITH A FEATURED SURFACE AND RELATED MANUFACTURING METHOD 失效
    冷却组件与特色表面及相关制造方法

    公开(公告)号：US20100119372A1

    公开(公告)日：2010-05-13

    申请号：US12270372

    申请日：2008-11-13

    申请人： Raymond Gage ,  Adrian Allan

    发明人： Raymond Gage ,  Adrian Allan

    IPC分类号： F04D29/38 ,  B23P15/02

    CPC分类号： B23P15/02 ,  F01D5/187 ,  F05D2260/202 ,  F05D2260/22141 ,  F05D2300/5024 ,  F23R2900/03045 ,  Y10T29/49336

    摘要： An improved type of cooled component is disclosed. The cooled components, such as turbine airfoils and combustors, have a base metal structural member, including a metal sheet or blank, with a featured surface. The features, such as fins, pins, and other protrusions, as well as divots, indentions, slots, channels, and holes, are formed by lithographic processes. The protrusions can be formed from a different material than the metal sheet or blank, preferably one with superior heat-conductive or oxidation properties. A related method of manufacturing is also disclosed.

    摘要翻译： 公开了一种改进型的冷却部件。 诸如涡轮机翼型和燃烧器的冷却部件具有贱金属结构件，包括具有特征表面的金属板或坯件。 通过光刻工艺形成诸如翅片，销和其它突起以及凹陷，凹陷，槽，通道和孔的特征。 突起可以由与金属板或坯料不同的材料形成，优选地具有优异的导热性或氧化性。 还公开了相关的制造方法。

    VARIABLE TURBINE COOLING FLOW SYSTEM
    5.
    发明申请
    VARIABLE TURBINE COOLING FLOW SYSTEM 失效
    可变涡轮冷却流量系统

    公开(公告)号：US20050132711A1

    公开(公告)日：2005-06-23

    申请号：US10739754

    申请日：2003-12-17

    申请人： Peter Morgan ,  William Howe ,  Mark Morris ,  Adrian Allan ,  Donald Palmer

    发明人： Peter Morgan ,  William Howe ,  Mark Morris ,  Adrian Allan ,  Donald Palmer

    IPC分类号： F01D17/14 ,  F02C7/18 ,  F02C9/20 ,  F02C1/00

    CPC分类号： F02C9/20 ,  F01D17/141 ,  F02C7/18 ,  F05D2240/55 ,  F05D2240/57 ,  F05D2250/61 ,  Y10T137/7781

    摘要： Cooling air to the blades and disks of a gas turbine may be modulated to provide a variable turbine cooling flow. A bellows may be extended by providing a high pressure compressor discharge flow to an interior of the bellows. The bellows may be compressed when the interior of the bellows communicates with ambient pressure air. The extension/compression of the bellows moves an arm over orifices in a cooling air flow path. The pressure inside of the bellows is metered to move the arm over at least one orifice, thereby restricting cooling air flow when the engine is running at low power. The pressure inside of the bellows is metered to move the arm to uncover all of the slots to provide maximum cooling flow when the engine is running at high power. The resulting variable cooling flow system results in less need for cooling air at low powers, thus reducing engine fuel consumption.

    摘要翻译： 可以调节到燃气轮机的叶片和盘的冷却空气以提供可变的涡轮机冷却流。 通过向波纹管的内部提供高压压缩机排出流，可以延伸波纹管。 当波纹管内部与环境压力空气相通时，波纹管可能被压缩。 波纹管的延伸/压缩将臂移动到冷却空气流动路径中的孔口上。 波纹管内部的压力被计量以将臂移动至少一个孔口，从而在发动机以低功率运行时限制冷却气流。 波纹管内部的压力被计量以移动臂以露出所有的槽，以在发动机以高功率运行时提供最大的冷却流量。 所产生的可变冷却流系统导致在低功率下对冷却空气的需求较少，从而降低发动机燃料消耗。